MH 114 13.02% (mh114-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MH 114 13.02% (mh114-il) Reynolds number: 1,000,000 Max Cl/Cd: 160.95 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mh114-il-1000000.txt Download as CSV file: xf-mh114-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MH 114 13.02%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.250 -0.0190 0.11055 0.10874 -0.1033 0.9678 0.0103
-11.000 -0.0075 0.10677 0.10496 -0.1061 0.9642 0.0106
-10.750 0.0026 0.10232 0.10050 -0.1099 0.9596 0.0109
-10.500 0.0149 0.09814 0.09632 -0.1138 0.9540 0.0109
-10.250 0.0326 0.09392 0.09208 -0.1186 0.9505 0.0110
-10.000 0.0515 0.08972 0.08785 -0.1237 0.9456 0.0110
-9.750 0.0706 0.08471 0.08282 -0.1297 0.9405 0.0111
-9.500 0.0985 0.08149 0.07957 -0.1356 0.9368 0.0114
-9.250 0.1246 0.07760 0.07564 -0.1422 0.9290 0.0114
-8.750 0.1703 0.07094 0.06884 -0.1528 0.9071 0.0121
-8.500 0.1817 0.06788 0.06570 -0.1555 0.8929 0.0124
-8.250 0.1883 0.06500 0.06277 -0.1571 0.8795 0.0127
-8.000 0.1913 0.06191 0.05963 -0.1583 0.8670 0.0130
-7.750 0.1843 0.05662 0.05430 -0.1605 0.8538 0.0137
-7.500 0.1770 0.05238 0.05002 -0.1614 0.8418 0.0138
-7.250 0.0810 0.02086 0.01744 -0.1878 0.8189 0.0081
-7.000 0.0989 0.01683 0.01281 -0.1897 0.8123 0.0077
-6.750 0.1229 0.01451 0.01007 -0.1905 0.8069 0.0074
-6.500 0.1491 0.01318 0.00849 -0.1909 0.8014 0.0073
-6.250 0.1761 0.01228 0.00739 -0.1912 0.7961 0.0074
-6.000 0.2036 0.01157 0.00653 -0.1914 0.7910 0.0074
-5.750 0.2314 0.01096 0.00582 -0.1916 0.7857 0.0076
-5.500 0.2594 0.01048 0.00522 -0.1918 0.7805 0.0079
-5.250 0.2877 0.01009 0.00473 -0.1920 0.7755 0.0082
-5.000 0.3162 0.00956 0.00411 -0.1923 0.7702 0.0089
-4.750 0.3445 0.00927 0.00377 -0.1925 0.7649 0.0097
-4.500 0.3729 0.00907 0.00350 -0.1927 0.7599 0.0107
-4.250 0.4016 0.00874 0.00313 -0.1929 0.7545 0.0118
-4.000 0.4299 0.00857 0.00291 -0.1930 0.7491 0.0136
-3.750 0.4585 0.00836 0.00266 -0.1932 0.7438 0.0168
-3.500 0.4872 0.00815 0.00245 -0.1934 0.7384 0.0223
-3.250 0.5155 0.00800 0.00231 -0.1935 0.7327 0.0317
-3.000 0.5439 0.00787 0.00219 -0.1936 0.7273 0.0443
-2.750 0.5724 0.00771 0.00209 -0.1938 0.7215 0.0631
-2.500 0.6006 0.00757 0.00201 -0.1940 0.7157 0.0894
-2.250 0.6292 0.00744 0.00195 -0.1942 0.7102 0.1210
-2.000 0.6576 0.00731 0.00190 -0.1944 0.7039 0.1578
-1.750 0.6855 0.00723 0.00187 -0.1945 0.6979 0.1989
-1.500 0.7141 0.00710 0.00186 -0.1948 0.6919 0.2439
-1.250 0.7421 0.00703 0.00185 -0.1949 0.6853 0.2855
-1.000 0.7700 0.00698 0.00186 -0.1949 0.6790 0.3268
-0.750 0.7982 0.00691 0.00188 -0.1951 0.6722 0.3735
-0.500 0.8255 0.00690 0.00191 -0.1950 0.6652 0.4191
-0.250 0.8536 0.00685 0.00195 -0.1952 0.6581 0.4625
0.000 0.8806 0.00687 0.00199 -0.1950 0.6506 0.5017
0.250 0.9085 0.00686 0.00204 -0.1950 0.6434 0.5396
0.500 0.9352 0.00689 0.00211 -0.1949 0.6354 0.5760
0.750 0.9626 0.00690 0.00218 -0.1948 0.6276 0.6117
1.000 0.9890 0.00696 0.00225 -0.1945 0.6193 0.6463
1.250 1.0160 0.00698 0.00233 -0.1944 0.6110 0.6819
1.500 1.0416 0.00706 0.00243 -0.1939 0.6022 0.7178
1.750 1.0682 0.00708 0.00253 -0.1937 0.5935 0.7558
2.000 1.0930 0.00715 0.00264 -0.1931 0.5846 0.7975
2.250 1.1170 0.00717 0.00275 -0.1923 0.5750 0.8482
2.500 1.1339 0.00712 0.00283 -0.1898 0.5664 0.9340
2.750 1.1586 0.00721 0.00289 -0.1892 0.5561 1.0000
3.000 1.1846 0.00736 0.00299 -0.1889 0.5464 1.0000
3.250 1.2094 0.00754 0.00312 -0.1884 0.5363 1.0000
3.500 1.2342 0.00772 0.00324 -0.1879 0.5255 1.0000
3.750 1.2590 0.00789 0.00337 -0.1874 0.5152 1.0000
4.000 1.2827 0.00810 0.00351 -0.1867 0.5045 1.0000
4.250 1.3064 0.00831 0.00368 -0.1859 0.4932 1.0000
4.500 1.3301 0.00851 0.00383 -0.1853 0.4823 1.0000
4.750 1.3526 0.00874 0.00401 -0.1843 0.4715 1.0000
5.000 1.3739 0.00897 0.00420 -0.1831 0.4604 1.0000
5.250 1.3956 0.00919 0.00438 -0.1821 0.4494 1.0000
5.500 1.4162 0.00944 0.00459 -0.1808 0.4389 1.0000
6.000 1.4570 0.00997 0.00504 -0.1782 0.4172 1.0000
6.250 1.4769 0.01026 0.00529 -0.1768 0.4066 1.0000
6.750 1.5158 0.01086 0.00583 -0.1740 0.3854 1.0000
7.000 1.5350 0.01119 0.00613 -0.1725 0.3755 1.0000
7.500 1.5716 0.01190 0.00678 -0.1694 0.3542 1.0000
7.750 1.5896 0.01229 0.00714 -0.1679 0.3442 1.0000
8.250 1.6239 0.01313 0.00792 -0.1645 0.3234 1.0000
8.500 1.6403 0.01359 0.00837 -0.1628 0.3134 1.0000
9.000 1.6719 0.01461 0.00934 -0.1593 0.2924 1.0000
9.250 1.6867 0.01517 0.00988 -0.1574 0.2826 1.0000
9.750 1.7147 0.01644 0.01110 -0.1536 0.2613 1.0000
10.000 1.7282 0.01713 0.01177 -0.1517 0.2508 1.0000
10.250 1.7401 0.01793 0.01254 -0.1496 0.2405 1.0000
10.500 1.7520 0.01874 0.01333 -0.1476 0.2294 1.0000
10.750 1.7643 0.01956 0.01414 -0.1457 0.2191 1.0000
11.000 1.7746 0.02053 0.01508 -0.1436 0.2087 1.0000
11.250 1.7835 0.02162 0.01613 -0.1415 0.1973 1.0000
11.500 1.7937 0.02264 0.01715 -0.1395 0.1872 1.0000
11.750 1.8028 0.02379 0.01828 -0.1376 0.1771 1.0000
12.000 1.8105 0.02507 0.01953 -0.1355 0.1670 1.0000
12.250 1.8163 0.02651 0.02094 -0.1334 0.1560 1.0000
12.500 1.8236 0.02790 0.02232 -0.1315 0.1463 1.0000
12.750 1.8305 0.02936 0.02378 -0.1296 0.1375 1.0000
13.000 1.8356 0.03102 0.02542 -0.1278 0.1288 1.0000
13.250 1.8420 0.03263 0.02703 -0.1261 0.1208 1.0000
13.500 1.8467 0.03442 0.02882 -0.1244 0.1128 1.0000
13.750 1.8495 0.03645 0.03084 -0.1226 0.1047 1.0000
14.000 1.8542 0.03836 0.03275 -0.1212 0.0972 1.0000
14.250 1.8562 0.04057 0.03497 -0.1196 0.0891 1.0000
14.500 1.8565 0.04305 0.03743 -0.1182 0.0816 1.0000
14.750 1.8590 0.04537 0.03977 -0.1169 0.0751 1.0000
15.000 1.8593 0.04799 0.04240 -0.1157 0.0684 1.0000
15.250 1.8583 0.05082 0.04522 -0.1146 0.0623 1.0000
15.500 1.8593 0.05351 0.04795 -0.1137 0.0570 1.0000
15.750 1.8574 0.05663 0.05108 -0.1128 0.0520 1.0000
16.000 1.8573 0.05961 0.05411 -0.1122 0.0478 1.0000
16.250 1.8547 0.06297 0.05750 -0.1116 0.0437 1.0000
16.500 1.8536 0.06622 0.06081 -0.1112 0.0402 1.0000
16.750 1.8499 0.06990 0.06452 -0.1110 0.0367 1.0000
17.000 1.8482 0.07339 0.06808 -0.1109 0.0338 1.0000
17.250 1.8430 0.07744 0.07217 -0.1109 0.0310 1.0000
17.500 1.8411 0.08108 0.07589 -0.1110 0.0287 1.0000
17.750 1.8348 0.08543 0.08030 -0.1114 0.0263 1.0000
18.000 1.8307 0.08956 0.08450 -0.1118 0.0243 1.0000
18.250 1.8248 0.09401 0.08901 -0.1125 0.0223 1.0000
18.500 1.8182 0.09860 0.09369 -0.1133 0.0206 1.0000
18.750 1.8125 0.10312 0.09829 -0.1142 0.0190 1.0000
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Polar data table (+)
Polar graphs
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